WO2011090083A1 - タービン動翼及びターボ機械 - Google Patents
タービン動翼及びターボ機械 Download PDFInfo
- Publication number
- WO2011090083A1 WO2011090083A1 PCT/JP2011/050889 JP2011050889W WO2011090083A1 WO 2011090083 A1 WO2011090083 A1 WO 2011090083A1 JP 2011050889 W JP2011050889 W JP 2011050889W WO 2011090083 A1 WO2011090083 A1 WO 2011090083A1
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- WIPO (PCT)
- Prior art keywords
- blade
- tip
- shroud
- turbine
- tip shroud
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a plurality of turbine rotor blades arranged at predetermined intervals in the circumferential direction of a rotating shaft, and a turbomachine equipped with the turbine rotor blades.
- a gas turbine for power generation which is a kind of turbomachine, includes a compressor, a combustor, and a turbine.
- the air taken in from the air intake port is compressed by the compressor to become high-temperature and high-pressure compressed air.
- the combustor the fuel is supplied to the compressed air and burned, so that the high-temperature and high-pressure is burned.
- the combustion gas (working fluid) is obtained, the turbine is driven by the combustion gas, and the generator connected to the turbine is driven.
- the first stage blade and the second stage blade in the front stage are short in the blade height direction (radial direction on the rotating shaft), but the rear stage three stage blade and The four-stage blade (final blade) has a long blade length (long blade) in terms of performance.
- a tip shroud is attached to the tip, and tip shrouds of adjacent blades are brought into contact with each other to form an annular shape. Forming a shroud.
- a turbine rotor blade of the present invention is a plurality of turbine rotor blades arranged at a predetermined interval in the circumferential direction of a rotating shaft, and a blade body whose base end is fixed to the rotating shaft;
- a tip shroud provided at the tip of the wing body so as to constitute a part of a ring-shaped shroud, and the meridional shape of the leading edge side of the wing body is curved to the trailing edge side
- a fillet is provided between the tip of the wing body and the inner surface of the tip shroud, and the curved portion is located on the front edge side of the fillet. It is characterized by.
- a curved portion is provided on the leading end side of the leading edge of the wing body, and a tip shroud is provided through the curved portion, and the tip portion side of the wing body can be retracted to reduce weight.
- the pressure distribution on each surface of the blade main body and the tip shroud can be made appropriate, and the deterioration of the performance can be suppressed.
- the curved portion protrudes to the front edge side from a straight line connecting the front ends of the fillets provided on both sides of the blade body.
- connection position between the curved portion and the outer surface of the tip shroud is front and rear of the blade body from the front edge to the rear edge side of the blade body along the axial direction of the rotating shaft. It is characterized by being set at a position that is at least 10% of the length.
- the tip shroud has seal fins along the circumferential direction on the outer surface, and the connection position between the curved portion and the outer surface of the tip shroud is along the axial direction of the rotating shaft. It is characterized by being set equal to the front end face of the seal fin or at a position on the front edge side of the blade body from the seal fin.
- connection position between the leading edge of the blade main body and the curved portion is such that the blade main body extends from the front end portion to the base end side of the blade main body along the radial direction of the rotating shaft. It is characterized in that it is set at a position that is at least 20% of the length in the front-rear direction.
- the shape of the blade body can be optimized by retracting the tip of the blade body by an appropriate amount.
- connection position between the leading edge of the blade main body and the curved portion is such that the blade main body extends from the front end portion to the base end side of the blade main body along the radial direction of the rotating shaft. And it is set to the position below 20% length in the height of a chip shroud.
- the shape of the blade body can be optimized by retracting the tip of the blade body by an appropriate amount.
- the pressure distribution on each surface of the blade body and the tip shroud is made appropriate, and the weight of the blade tip can be reduced without degrading performance.
- I can plan. That is, in the past, a complicated flow due to the influence of the concave portion collided with the chip shroud to cause a loss, but the front of the chip shroud that does not contribute to aerodynamics without performing work as a turbine blade. By retreating the edge, collision with the flow can be mitigated to prevent the performance from deteriorating, and the weight can be reduced.
- the tip shroud has a long plate shape along the circumferential direction of the shroud, and a narrow width portion is provided in an area where the blade body is not present.
- the turbine rotor blade of the present invention is a plurality of turbine rotor blades arranged at predetermined intervals in the circumferential direction of the rotating shaft, and has an annular shape with a blade body whose base end is fixed to the rotating shaft.
- a tip shroud provided at the tip of the wing body so as to constitute a part of the shroud, and a curved shape in which the tip of the leading edge of the wing body curves toward the trailing edge, and the tip shroud It projects from the outer surface to the upstream side of the gas flow path.
- tip the leading edge tip portion of the blade body is protruded upstream of the gas flow path
- a turbo machine according to the present invention includes the above-described turbine rotor blade.
- a curved portion is provided on the leading end side of the leading edge of the wing body, and a tip shroud is provided through the curved portion, and the tip portion side of the wing body can be retracted to reduce weight.
- the pressure distribution on each surface of the blade main body and the tip shroud can be made appropriate, and degradation in performance can be suppressed.
- the front end side of the front edge of the blade body is provided with a curved portion, and the tip shroud is provided through the curved portion, thereby retreating the front end portion side of the blade body.
- the flow of the working fluid can be made smooth, the pressure distribution on each surface of the blade main body and the tip shroud can be made appropriate, and deterioration in performance can be suppressed.
- FIG. 1 is a plan view showing a turbine rotor blade according to an embodiment of the present invention.
- FIG. 2 is a side view showing the turbine rotor blade of the present embodiment and is a cross-sectional view taken along the line II-II in FIG.
- FIG. 3 is a front view showing the turbine rotor blade of the present embodiment.
- FIG. 4 is a schematic view showing the tip portion of the turbine rotor blade of the present embodiment.
- FIG. 5 is a schematic diagram showing an assembled state of the turbine rotor blade of the present embodiment.
- FIG. 6 is a schematic diagram showing the turbine rotor blade of the present embodiment.
- FIG. 7 is a schematic diagram showing the flow of combustion gas (working fluid) in a conventional turbine rotor blade.
- FIG. 1 is a plan view showing a turbine rotor blade according to an embodiment of the present invention.
- FIG. 2 is a side view showing the turbine rotor blade of the present embodiment and is a cross-sectional view taken along the line II
- FIG. 8 is a schematic diagram showing the flow of combustion gas (working fluid) in the turbine rotor blade of the present embodiment.
- FIG. 9 is a schematic view showing a gas turbine to which the turbine rotor blade of the present embodiment is applied.
- FIG. 10 is a schematic diagram for supplementing the shape explanation of the turbine rotor blade of the present embodiment.
- FIG. 1 is a plan view showing a turbine blade according to an embodiment of the present invention
- FIG. 2 is a side view showing the turbine blade of this embodiment, and is a cross-sectional view taken along the line II-II in FIG.
- FIG. 4 is a schematic view showing a tip portion of the turbine rotor blade of the present embodiment
- FIG. 5 is a schematic view showing an assembled state of the turbine rotor blade of the present embodiment.
- 6 is a schematic diagram showing the turbine rotor blade of this embodiment
- FIG. 7 is a schematic diagram showing the flow of combustion gas (working fluid) in the conventional turbine rotor blade
- FIG. 8 is the turbine motion of this embodiment.
- FIG. 9 is a schematic diagram showing the flow of combustion gas (working fluid) in the blades
- FIG. 9 is a schematic diagram showing a gas turbine to which the turbine rotor blade of the present embodiment is applied
- 10 is a shape explanation in the turbine rotor blade of the present embodiment. It is the schematic for supplementing.
- the gas turbine of this embodiment is composed of a compressor 11, a combustor 12, and a turbine 13, as shown in FIG.
- a generator (not shown) is connected to the gas turbine and can generate power.
- the compressor 11 has an air intake 21 for taking in air, and a plurality of stationary blades 23 and moving blades 24 are alternately arranged in the front and rear direction (the axial direction of a rotor 32 described later) in a compressor casing 22.
- the bleed chamber 25 is provided on the outer side.
- the combustor 12 is combustible by supplying fuel to the compressed air compressed by the compressor 11 and igniting it.
- a plurality of stationary blades 27 and moving blades 28 are alternately disposed in a turbine casing 26 in the front-rear direction (the axial direction of a rotor 32 described later).
- An exhaust chamber 30 is disposed downstream of the turbine casing 26 via an exhaust casing 29, and the exhaust chamber 30 has an exhaust diffuser 31 that is continuous with the turbine 13.
- a rotor (rotary shaft) 32 is positioned so as to penetrate through the center of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 30.
- the end of the rotor 32 on the compressor 11 side is rotatably supported by the bearing portion 33, while the end of the exhaust chamber 30 side is rotatably supported by the bearing portion 34.
- the rotor 32 is fixed by stacking a plurality of disks with each blade 24 mounted thereon by the compressor 11 and fixed by a plurality of disks having each blade 28 mounted by the turbine 13.
- a generator drive shaft (not shown) is connected to the end on the exhaust chamber 30 side.
- the compressor casing 22 of the compressor 11 is supported by the legs 35
- the turbine casing 26 of the turbine 13 is supported by the legs 36
- the exhaust chamber 30 is supported by the legs 37.
- the air taken in from the air intake 21 of the compressor 11 passes through the plurality of stationary blades 23 and the moving blades 24 and is compressed to become high-temperature and high-pressure compressed air.
- a predetermined fuel is supplied to the compressed air in the combustor 12 and burned.
- the high-temperature and high-pressure combustion gas (working fluid) that is the working fluid generated by the combustor 12 passes through the plurality of stationary blades 27 and the moving blades 28 that constitute the turbine 13 to drive and rotate the rotor 32.
- the generator connected to the rotor 32 is driven.
- the energy of the exhaust gas (combustion gas) is converted into pressure by the exhaust diffuser 31 in the exhaust chamber 30 and decelerated before being released to the atmosphere.
- the moving blade 28 has a blade root portion 41 fixed to the disk (rotor 32) and a base end portion joined to the blade root portion 41.
- the blade body 42 is twisted by a predetermined angle. Yes.
- a plurality of blade root portions 41 are fitted to the outer peripheral portion of the disk along the circumferential direction so that the tip shrouds 43 are in contact with each other and connected to each other, and a shroud having an annular shape on the outer peripheral side. 45 is configured.
- the casing 46 constituting the turbine casing 26 has an inner surface in the flow direction of the combustion gas (working fluid).
- a gas flow passage 47 having a cylindrical shape that becomes wider toward the downstream side (right side in FIG. 2) is formed, and an inclined surface 46a and an annular groove (concave portion) 46b are formed on the inner surface.
- the base end portion of the stationary blade 27 is fixed to the inclined surface 46a, while the tip portion of the moving blade 28 is disposed in the annular groove 46b.
- a predetermined gap is secured between the groove 46b.
- the inclined surface 46a of the casing 46 and the outer surface 43A of the tip shroud 43 of the rotor blade 28 are set at a substantially linear position, but the radial direction according to the flow of combustion gas (working fluid) You may arrange
- the tip shroud 43 of the rotor blade 28 has a long plate shape along the circumferential direction of the shroud 45, and the leading edge side of the rotor 32 is located in a region where the blade body 42 is not connected.
- Notches 43a and 43b are formed indented in the axial direction (rotational axis direction) rear side along the rotational direction, and the rear edge side is directed in the axial direction (rotational axis direction) front side along the rotational direction of the rotor 32.
- Indented notches 43c and 43d are formed. That is, the chip shroud 43 is a so-called partial cover in which narrow portions (notches 43a, 43b, 43c, 43d) are provided in part.
- a cross-sectional arc shape is formed between the tip end portion of the blade body 42 and the inner surface 43 ⁇ / b> B of the tip shroud 43 on both sides in the circumferential direction of the blade body 42.
- Fillets (fillets) 51a and 51b are provided, and the wing body 42 and the tip shroud 43 are continuous with a smooth curved surface without a step.
- the fillets 51a and 51b are provided in a region excluding the front edge side and the rear edge side of the wing body 42, and have an elliptical shape (see FIG. 1) when viewed from the outer surface 43A side of the tip shroud 43.
- the blade body 42 has a leading edge 52 and a trailing edge 53, and each edge 52, 53 is formed by a curved surface in the thickness direction of the blade body 42.
- the leading edge 52 is a straight line in which the tip side of the blade body 42 is inclined rearward (rear edge 53 side) with respect to the radial direction orthogonal to the axial direction of the rotor 32 and the meridional surface shape is substantially linear.
- the trailing edge 53 is a straight portion in which the meridional surface shape along the radial direction orthogonal to the axial center direction of the rotor 32 is substantially linear.
- the front edge 52 and the rear edge 53 are preferably formed in a straight line, but may be formed in a curved line that approximates a straight line as necessary.
- the leading edge 52 of the blade body 42 is continuous with the outer surface 43A of the tip shroud 43 via a curved portion 54 whose meridional shape on the tip end side curves toward the trailing edge 53 side.
- the curved portion 54 is located closer to the front edge 52 than the fillets 51a and 51b. That is, the front edge 52 of the blade main body 42 is curved to the outer surface 43A of the tip shroud 43 by retreating the connecting portion (connection position) with the tip shroud 43 at the front edge 52 to the rear edge 53 side. There is no step through the portion 54 and it is smoothly continuous.
- the curved portion 54 has a shape that protrudes toward the front edge 52 from the straight line A connecting the front ends of the fillets 51a and 51b provided on both sides of the wing body 42.
- the curved portion 54 when the curved portion 54 is positioned on the front edge 52 side from the fillets 51a and 51b, or the curved portion 54 protrudes on the front edge 52 side from the straight line A (see FIG. 1) connecting the front ends of the fillets 51a and 51b. This means that it is located on the front edge 52 side with respect to a plane orthogonal to the axial direction of the rotor 32.
- the curved portion 54 is formed so as to continue from the front edge 52 of the wing body 42 and further to the outer surface 43A of the tip shroud 43, so that the thickness of the wing body 42 is the same as that of the front edge 52. It is formed by a curved surface in the vertical direction, and is a curved surface portion that curves in a three-dimensional direction. Further, the chip shroud 43 is a flat surface in which the outer surface 43A and the inner surface 43B are substantially linear with a predetermined angle with respect to the axial direction of the rotor 32, and have a curved shape with respect to the circumferential direction of the rotor 32. It is a curved surface.
- the curved portion 54 is formed by one or more arcs when viewed from the side of the wing body 42 (in the direction of FIG. 2), and one end is continuous with the front edge 52 of the wing body 42 at the intersection point a. The end is connected to the outer surface 43A of the tip shroud 43 at the intersection b. Further, an intersection 52a between the extension line of the leading edge 52 of the wing body 42 and the extension surface of the outer surface 43A of the tip shroud 43, and the extension line of the rear edge 53 of the wing body 42 and the extension surface of the outer surface 43A of the tip shroud 43.
- the intersection point 53a is set, the length in the axial direction of the rotor 32 between the intersection point 52a and the intersection point 53a is defined as a blade front-rear length L at the tip of the blade body 42.
- connection position (intersection point b) between the curved portion 54 and the outer surface 43A of the tip shroud 43 is moved from the front edge 52 of the blade body 42 toward the rear edge 53 along the axial direction of the rotor 32. It is desirable to set it to a position that is 10% or more of the length L1 in the front-rear length L of the blade. Further, the connection position (intersection point b) between the curved portion 54 and the outer surface 43A of the tip shroud 43 is equal to or equal to the front end surface 44a of the seal fin 44 in the axial direction of the rotor 32, or from the front end surface 44a of the seal fin 44.
- the length L1 may be replaced with the length between the intersection point b and the intersection point 52a, or may be replaced with the distance between the intersection point a and the intersection point b in the gas flow path direction.
- the fillets 51a and 51b are formed by one or more arcs when viewed from the front of the wing body 42 (direction of FIG. 3), and one end intersects with one side surface of the wing body 42 and intersects lines c and d. The other end is connected to the inner surface 43B of the chip shroud 43 by the intersection lines e and f.
- the length from the outer surface 41 a ′ of the platform 41 a of the blade body 42 to the outer surface 43 A of the tip shroud 43 is defined as a blade height (height of the blade body 42 and the tip shroud 43) H.
- connection position (intersection point a) between the leading edge 52 of the blade main body 42 and the curved portion 54 is changed from the distal end portion of the blade main body 42 toward the base end side along the radial direction of the rotor 32. It is set to a position (height H1) that is 20% or more of the front-rear length L at the tip. That is, as shown in detail in FIG. 10, it is desirable to set the length of H3-H1 to be 20% or more of the front-rear length L at the tip of the blade body 42.
- connection position (intersection point a) between the leading edge 52 of the blade main body 42 and the curved portion 54 is at the blade height H from the distal end portion to the proximal end portion side of the blade main body 42 along the radial direction of the rotor 32. It is set at a position (height H2) of 20% or less. That is, it is desirable to set the length of H3-H1 to 20% or less of the blade height H. Further, the length H3-H1 may be replaced with the length between the intersection point a and the intersection point 52a, or may be replaced with the distance between the blade height direction between the intersection point a and the intersection point b. H3 is the length from the outer surface 41a 'of the platform 41a of the wing body 42 to the intersection 52a.
- the combustion gas flowing through the gas flow path 47 has an absolute velocity Va, and the turbine rotor blade 28 rotates in the direction of arrow R. Therefore, assuming that the rotation velocity Vr, combustion on the blade body 42 and the tip shroud 43 is performed. A relative gas velocity Vb is defined.
- the combustion gas flowing through the gas flow path 47 flows along the inclined surface 46 a of the casing 46 in the region B by the annular groove 46 b and the tip of the blade body 42 and the tip shroud 43. Prone to turbulence.
- the leading edge 003 of the blade body 001 extends substantially linearly toward the tip end side, and the tip shroud 002 is disposed at the tip end.
- the blade body 001 of the combustion gas is formed due to the axial gap formed here. The flow toward is slow. Then, the absolute velocity Va1 of the combustion gas flowing through the gas flow path 47 is reduced, and the rotational speed Vr of the turbine rotor blade 28 does not change. Therefore, the relative velocity Vb1 of the combustion gas with respect to the blade body 42 and the tip shroud 43 is also reduced.
- That direction will also change. That is, the combustion gas flows toward the back side 001b with respect to the leading edge 003 of the blade main body 001. In the blade main body 001, the pressure on the back side 001b increases and the pressure on the ventral side 001a decreases. Therefore, a force in the direction opposite to the rotation direction R acts. Then, as the force in the direction opposite to the rotation direction of the turbine rotor blade 28 acts, the work performed by the turbine is lost, the output is reduced, and the performance is deteriorated.
- the leading edge 52 of the blade body 42 is smoothly continuous with the tip shroud 43 by the curved portion 54. Is retracted on the tip side, the front edge of the wing body 42 is moved away from this region B, and the portion of the wing body 42 where a force in the direction opposite to the rotational direction acts is reduced. Therefore, the absolute velocity Va of the combustion gas flowing through the gas flow path 47 is increased, and the relative velocity Vb of the combustion gas with respect to the blade main body 42 and the tip shroud 43 is increased when the rotational speed Vr of the turbine rotor blade 28 is taken into consideration.
- the combustion gas flows toward the ventral side 42a with respect to the leading edge 52 of the wing body 42, and the wing body 42 has a pressure on the ventral side 42a higher than the pressure on the back side 42b.
- a force in the same direction as the rotation direction R acts. Then, the combustion gas flows smoothly, the friction between the blade main body 42 and the tip shroud 43 is reduced, the loss is reduced, and the performance deterioration is suppressed.
- a plurality of rotor blades 28 are arranged at predetermined intervals in the circumferential direction of the rotor 32, and the rotor blades 28 are blade root portions 41 fixed to the rotor 32, A blade main body 42 having a base end portion connected to the blade root portion 41, and a tip shroud 43 connected to a distal end portion of the blade main body 42 so as to constitute a part of the annular shroud 43;
- the front end portion side of the front edge 52 in the main body 42 is connected to the outer surface 43A of the tip shroud 43 via a curved portion 54 that curves to the rear edge 53 side, and between the front end portion of the blade main body 42 and the inner surface 43B of the tip shroud 43.
- Fillets 51a and 51b are provided, and the curved portion 54 is positioned closer to the front edge 52 than the fillets 51a and 51b.
- a curved portion 54 is provided on the tip end side of the leading edge 52 in the wing body 42, a tip shroud 43 is provided through the curved portion 54, and the curved portion 54 is positioned closer to the leading edge 52 than the fillets 51a and 51b.
- the tip end side of the wing body 42 is retracted, and the tip shroud 43 provided on the tip end side of the wing body 42 can be reduced in weight.
- the curved portion 54 the combustion gas flows smoothly, the pressure distribution on each surface of the blade main body 42 and the tip shroud 43 becomes appropriate, and the performance degradation can be suppressed.
- the connecting position of the curved portion 54 and the outer surface 43A of the tip shroud 43 is changed from the front edge 52 of the blade body 42 toward the rear edge 53 side at the front and rear portions at the front end portion of the blade body 42.
- the position is set to a position from the position of 10% of the length L to the front end face 44 a of the seal fin 44. Therefore, the shape of the blade body 42, the tip shroud 43, and the seal fin 44 can be optimized by retracting the tip end side of the leading edge 52 of the blade body 42 by an appropriate amount.
- the connecting position of the leading edge 52 of the blade body 42 and the curved portion 54 is changed from the front end portion of the blade main body 42 toward the base end portion in the front-rear direction of the front end portion of the blade main body 42.
- 20% of the height (blade height) H of the wing body 42 and the tip shroud 43 from the position of 20% of the length L toward the base end side from the distal end portion of the wing body 42 It is set up to the position. Therefore, the shape of the blade body 42, the tip shroud 43, and the seal fin 44 can be optimized by retracting the tip end side of the leading edge 52 of the blade body 42 by an appropriate amount.
- annular groove 46 b is provided on the inner surface of the casing 46 facing the shroud 45. Therefore, the gas flow in the region between the casing 46 and the blade body 42 and the tip shroud 43 can be made smooth, the pressure distribution on each surface of the blade body 42 and the tip shroud 43 is made appropriate, and deterioration in performance is suppressed. Can do.
- the tip shroud 43 has a long plate shape along the circumferential direction of the shroud 45, and notches 43a, 43b, 43c, 43d are formed in regions where the blade body 42 is not provided. It can be possible to reduce the weight.
- the stationary blades 27 and the moving blades 28 are alternately arranged along the flow direction of the working fluid (combustion gas).
- the blade main body 42 and the tip shroud 43 are provided, and the front end portion side of the leading edge 52 in the blade main body 42 is connected to the outer surface 43A of the tip shroud 43 via a curved portion 54 curved to the rear edge 53 side.
- Fillets 51a and 51b are provided between the front end portion and the inner surface 43B of the tip shroud 43, and the curved portion 54 is positioned closer to the front edge 52 than the fillets 51a and 51b.
- a curved portion 54 is provided on the tip end side of the leading edge 52 in the wing body 42, a tip shroud 43 is provided through the curved portion 54, and the curved portion 54 is positioned closer to the leading edge 52 than the fillets 51a and 51b.
- the tip end side of the wing body 42 is retracted, and the wing body 42 can be reduced in weight.
- the working fluid combustion gas
- the pressure distribution on each surface of the blade main body 42 and the tip shroud 43 becomes appropriate, and the deterioration of the performance can be suppressed. As a result, turbine efficiency can be improved.
- the turbine rotor blade of the present invention is applied to a three-stage rotor blade or a four-stage rotor blade (final stage rotor blade).
- the present invention is not limited to this, and the rotor blade having a tip shroud is used. If it is.
- the gas turbine for electric power generation was demonstrated as a turbomachine, it is not limited to this, It can apply also to turbomachines, such as an aeronautical gas turbine and a steam turbine.
- the turbine rotor blade and the turbomachine according to the present invention have a curved shape in which the leading edge side of the leading edge of the blade body is curved toward the trailing edge, and is positioned on the leading edge side of the fillet or protrudes from the outer surface of the tip shroud.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
KR1020127013806A KR101305575B1 (ko) | 2010-01-20 | 2011-01-19 | 터빈 동익 및 터보 기계 |
CN201180004741.1A CN102639817B (zh) | 2010-01-20 | 2011-01-19 | 涡轮动叶片及涡轮机 |
JP2011550932A JP5297540B2 (ja) | 2010-01-20 | 2011-01-19 | タービン動翼及びターボ機械 |
EP11734689.0A EP2527596B1 (en) | 2010-01-20 | 2011-01-19 | Turbine rotor blade and turbo machine |
US13/508,689 US9194239B2 (en) | 2010-01-20 | 2011-01-19 | Turbine rotor blade and turbo machine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2010010361 | 2010-01-20 | ||
JP2010-010361 | 2010-01-20 |
Publications (1)
Publication Number | Publication Date |
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WO2011090083A1 true WO2011090083A1 (ja) | 2011-07-28 |
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ID=44306883
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/JP2011/050889 WO2011090083A1 (ja) | 2010-01-20 | 2011-01-19 | タービン動翼及びターボ機械 |
Country Status (6)
Country | Link |
---|---|
US (1) | US9194239B2 (ko) |
EP (1) | EP2527596B1 (ko) |
JP (1) | JP5297540B2 (ko) |
KR (1) | KR101305575B1 (ko) |
CN (1) | CN102639817B (ko) |
WO (1) | WO2011090083A1 (ko) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021199718A1 (ja) * | 2020-03-30 | 2021-10-07 | 株式会社Ihi | 二次流れ抑制構造 |
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CN103422906B (zh) * | 2013-08-29 | 2015-04-08 | 哈尔滨工程大学 | 一种具有s形叶冠动叶片的涡轮 |
CN107849926A (zh) * | 2015-07-24 | 2018-03-27 | 西门子公司 | 具有轮廓尖端罩的涡轮动叶片 |
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KR101874243B1 (ko) | 2017-03-31 | 2018-07-03 | 두산중공업 주식회사 | 버킷의 진동감쇠구조와 이를 포함하는 버킷 및 터보머신 |
JP7064076B2 (ja) * | 2018-03-27 | 2022-05-10 | 三菱重工業株式会社 | タービン翼及びタービン並びにタービン翼の固有振動数のチューニング方法 |
JP7162514B2 (ja) * | 2018-12-07 | 2022-10-28 | 三菱重工業株式会社 | 軸流式ターボ機械及びその翼 |
KR102610387B1 (ko) * | 2019-06-12 | 2023-12-05 | 미츠비시 파워 가부시키가이샤 | 로터 및 압축기 |
CN112443964B (zh) * | 2019-08-28 | 2022-09-13 | 青岛经济技术开发区海尔热水器有限公司 | 燃气热水器及其控制方法 |
JP7477284B2 (ja) * | 2019-11-14 | 2024-05-01 | 三菱重工業株式会社 | タービン翼及びガスタービン |
JP7360971B2 (ja) * | 2020-02-19 | 2023-10-13 | 三菱重工業株式会社 | タービン翼及びタービン |
EP4112884A1 (en) * | 2021-07-01 | 2023-01-04 | Doosan Enerbility Co., Ltd. | Blade for a turbomachine, blade assembly, and turbine |
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- 2011-01-19 KR KR1020127013806A patent/KR101305575B1/ko active IP Right Grant
- 2011-01-19 US US13/508,689 patent/US9194239B2/en active Active
- 2011-01-19 CN CN201180004741.1A patent/CN102639817B/zh active Active
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WO2021199718A1 (ja) * | 2020-03-30 | 2021-10-07 | 株式会社Ihi | 二次流れ抑制構造 |
JPWO2021199718A1 (ko) * | 2020-03-30 | 2021-10-07 | ||
US11808156B2 (en) | 2020-03-30 | 2023-11-07 | Ihi Corporation | Secondary flow suppression structure |
Also Published As
Publication number | Publication date |
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EP2527596B1 (en) | 2015-03-11 |
EP2527596A4 (en) | 2013-07-31 |
EP2527596A1 (en) | 2012-11-28 |
JP5297540B2 (ja) | 2013-09-25 |
KR101305575B1 (ko) | 2013-09-09 |
US9194239B2 (en) | 2015-11-24 |
US20120224974A1 (en) | 2012-09-06 |
CN102639817B (zh) | 2015-03-11 |
CN102639817A (zh) | 2012-08-15 |
JPWO2011090083A1 (ja) | 2013-05-23 |
KR20120075490A (ko) | 2012-07-06 |
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